station. Or, in another scenario, the orbital vehicle could shed its rectenna array for permanent use in space and be brought back as the return cargo on another interorbital vehicle to be retrofitted with another rectenna. The launching of missions that involve much hardware to the other planets or to the moon would be greatly facilitated by the proposed interorbital transfer system. REFERENCES 1. Final Proceedings of the Solar Power Satellite Program Review DOE/NASA Satellite Power System Concept Development and Evaluation Program, Conf. 800491, 1980. 2. B.I. Edelson, R.R. Marsten, and W.L. Morgan, Greater Message Capacity for Satellites, IEEE Spectrum, March, 56-64, 1982. 3. National Aeronautics and Space Administration, Design Definition of a Microwave Power Reception and Conversion System for Use on a HAPP, CR 156866, 1980. 4. W.C. Brown and J.F. Triner, Experimental Thin-Film, Etched-Circuit Rectenna, Paper K-4, IEEE MTT-S International Microwave Symposium Digest, IEEE Cat. No. 82CH 1705-3. 5. Lewis Research Center, Development of an Ultralight Large Area Printed Circuit Rectenna, LERC Contract NAS3-22764, Final Report CR168344, 1983. 6. NASA Wallops Flight Facility, A Design Study fora Ground Microwave Power Transmission System for Use on a High Altitude Powered Platform, Contract NAS6-3200 (in progress). 7. E. Stuhlinger, Ion Propulsion for Space Flight, Sec. 4.3, McGraw-Hill, NY (1964). 8. W.C. Brown, Microwave Beamed Power Technology Improvement, Final Report, JPL Contract 955104, 1980. 9. W.C. Brown, Satellite Power System (SPS) Magnetron Tube Assessment Study, NASA Contract NAS8-33157, 1981. 10. R.C. Finke, Electric Propulsion and Its Application to Space Missions, in Progress in Astronautics and Aeronautics, Vol. 79, American Institute of Aeronautics and Astronautics, NY (1981).
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